## 物理代写|空气动力学代写Aerodynamics代考|AES3530

statistics-lab™ 为您的留学生涯保驾护航 在代写空气动力学Aerodynamics方面已经树立了自己的口碑, 保证靠谱, 高质且原创的统计Statistics代写服务。我们的专家在代写空气动力学Aerodynamics代写方面经验极为丰富，各种代写空气动力学Aerodynamics相关的作业也就用不着说。

• Statistical Inference 统计推断
• Statistical Computing 统计计算
• Advanced Probability Theory 高等概率论
• Advanced Mathematical Statistics 高等数理统计学
• (Generalized) Linear Models 广义线性模型
• Statistical Machine Learning 统计机器学习
• Longitudinal Data Analysis 纵向数据分析
• Foundations of Data Science 数据科学基础

## 物理代写|空气动力学代写Aerodynamics代考|Compressible Unsteady Aerodynamics

The evaluation methods for the sectional as well as the total lift and moment coefficients for unsteady subsonic and supersonic flows will be given in Chap. 5. It is, however, possible to obtain approximate expressions for the amplitude of the sectional lift coefficients at high reduced frequencies and at transonic regimes where M approaches to unity as limiting value. For steady flow on the other hand, the analytical expression is not readily available since the equations are nonlinear. However, local linearization process is applied to obtain approximate values for the aerodynamic coefficients.

Now, we can give the expression for the amplitude of the sectional lift coefficient for a simple harmonically pitching thin airfoil in transonic flow,
$$\bar{c}_l \approx 4(1+i k) \bar{\alpha}, \quad k>1$$
Here, $\bar{\alpha}$ is the amplitude of the angle of attack. Let us consider the same airfoil in a vertical motion with amplitude of $\bar{h}$.
$$\bar{c}_l \approx 8 i k \bar{h} / b, \quad k>1$$
All these formulae are available from (Bisplinghoff et al. 1996).
Aerodynamic response to the arbitrary motion of a thin airfoil in transonic flow will be studied in Chap. 5 with aid of relevant unit response function in different Mach numbers.

## 物理代写|空气动力学代写Aerodynamics代考|Slender Body Aerodynamics

Munk-Jones airship theory is a good old useful tool for analyzing the aerodynamic behavior of slender bodies at small angles of attack even at supersonic speeds. The cross flow of a slender wing at a small angle of attack is approximately incompressible. Therefore, according to the Newton’s second law of motion, during the vertical motion of a slender body, the vertical momentum change of the air parcel with constant density displaced by the body motion is equal to the differential force acting on the body. Using this relation, we can decide on the aerodynamic stability of the slender body if we examine the sign of the aerodynamic moment about the center of gravity of the body. Expressing the change of the vertical force L, as a lifting force in terms of the cross sectional are $S$ and the equation of the axis $z=z_{\mathrm{a}}(x)$ of the body we obtain the following relation
$$\frac{d L}{d x}=-\rho U^2 \frac{d}{d x}\left(S \frac{d z_a}{d x}\right)$$
In Fig. 1.7, shown are the vertical forces affecting the slender body whose axis is at an angle of attack $\alpha$ with the free stream direction. Note that the vertical forces are non zero only at the nose and at the tail area because of the cross sectional area increase in those regions. Since there is no area change along the middle portion of the body, there is no vertical force generated at that portion of the body.

As we see in Fig. 1.7, the change of the moment with angle of attack taken around the center of gravity determines the stability of the body. The net moment of the forces acting at the nose and at the tail of the body counteracts with each other to give the sign of the total moment change with $\alpha$. The area increase at the tail section contributes to the stability as opposed to the apparent area increase at the nose region.

## 物理代写|空气动力学代写空气动力学代考|可压缩非定常空气动力学

$$\bar{c}_l \approx 8 i k \bar{h} / b, \quad k>1$$

## 物理代写|空气动力学代写空气动力学代考|细长体空气动力学

Munk-Jones飞艇理论是一个古老而有用的工具，用于分析细长物体在小迎角下的气动行为，甚至在超音速。细长翼在小迎角时的横流几乎是不可压缩的。因此，根据牛顿第二运动定律，在细长体的垂直运动过程中，密度恒定的空气块被物体运动所移位的垂直动量变化等于作用在物体上的微分力。利用这一关系式，考察细长体重心的气动力矩符号，就可以确定细长体的气动稳定性。将垂直力L的变化表示为横截面的升力$S$和体轴$z=z_{\mathrm{a}}(x)$的方程，我们得到如下关系
$$\frac{d L}{d x}=-\rho U^2 \frac{d}{d x}\left(S \frac{d z_a}{d x}\right)$$

## 有限元方法代写

tatistics-lab作为专业的留学生服务机构，多年来已为美国、英国、加拿大、澳洲等留学热门地的学生提供专业的学术服务，包括但不限于Essay代写，Assignment代写，Dissertation代写，Report代写，小组作业代写，Proposal代写，Paper代写，Presentation代写，计算机作业代写，论文修改和润色，网课代做，exam代考等等。写作范围涵盖高中，本科，研究生等海外留学全阶段，辐射金融，经济学，会计学，审计学，管理学等全球99%专业科目。写作团队既有专业英语母语作者，也有海外名校硕博留学生，每位写作老师都拥有过硬的语言能力，专业的学科背景和学术写作经验。我们承诺100%原创，100%专业，100%准时，100%满意。

## MATLAB代写

MATLAB 是一种用于技术计算的高性能语言。它将计算、可视化和编程集成在一个易于使用的环境中，其中问题和解决方案以熟悉的数学符号表示。典型用途包括：数学和计算算法开发建模、仿真和原型制作数据分析、探索和可视化科学和工程图形应用程序开发，包括图形用户界面构建MATLAB 是一个交互式系统，其基本数据元素是一个不需要维度的数组。这使您可以解决许多技术计算问题，尤其是那些具有矩阵和向量公式的问题，而只需用 C 或 Fortran 等标量非交互式语言编写程序所需的时间的一小部分。MATLAB 名称代表矩阵实验室。MATLAB 最初的编写目的是提供对由 LINPACK 和 EISPACK 项目开发的矩阵软件的轻松访问，这两个项目共同代表了矩阵计算软件的最新技术。MATLAB 经过多年的发展，得到了许多用户的投入。在大学环境中，它是数学、工程和科学入门和高级课程的标准教学工具。在工业领域，MATLAB 是高效研究、开发和分析的首选工具。MATLAB 具有一系列称为工具箱的特定于应用程序的解决方案。对于大多数 MATLAB 用户来说非常重要，工具箱允许您学习应用专业技术。工具箱是 MATLAB 函数（M 文件）的综合集合，可扩展 MATLAB 环境以解决特定类别的问题。可用工具箱的领域包括信号处理、控制系统、神经网络、模糊逻辑、小波、仿真等。

## 物理代写|空气动力学代写Aerodynamics代考|ASC4551

statistics-lab™ 为您的留学生涯保驾护航 在代写空气动力学Aerodynamics方面已经树立了自己的口碑, 保证靠谱, 高质且原创的统计Statistics代写服务。我们的专家在代写空气动力学Aerodynamics代写方面经验极为丰富，各种代写空气动力学Aerodynamics相关的作业也就用不着说。

• Statistical Inference 统计推断
• Statistical Computing 统计计算
• Advanced Probability Theory 高等概率论
• Advanced Mathematical Statistics 高等数理统计学
• (Generalized) Linear Models 广义线性模型
• Statistical Machine Learning 统计机器学习
• Longitudinal Data Analysis 纵向数据分析
• Foundations of Data Science 数据科学基础

## 物理代写|空气动力学代写Aerodynamics代考|Steady Aerodynamics of Thin Wings

The finite wing aerodynamics, for special wing geometries, can yield analytical expressions for the aerodynamic coefficients in terms of the sectional properties of the wing. A special case is the elliptical span wise loading of the wing which is proportional to $\sqrt{l^2-y^2}$, where $\mathrm{y}$ is the span wise coordinate and 1 is the half span. For the wings with large span, using the Prandtl’s lifting line theory the wing’s lift coefficient $C_L$ becomes equal to the constant sectional lift coefficient $c_l$. Hence,
$$C_L=c_l$$
Another interesting aspect of the finite wing theory is the effect of the tip vortices on the overall performance of the wing. The tip vortices induce a vertical velocity which in turn induces additional drag on the wing. Hence, the total drag coefficient of the wing reads
$$C_D=C_{D_o}+\frac{C_L^2}{\pi A R}$$
Here the aspect ratio is $A R=l^2 / S$, and $\mathrm{S}$ is the wing area. For the symmetric and untwisted wings to have elliptical loading the plan form geometry also should be elliptical as shown in Fig. 1.3.

For the case of non-elliptical wings, we use the Glauert’s Fourier series expansion of the span wise variation of the circulation given by the lifting line theory. The integration of the numerically obtained span wise distribution of the circulation gives us the total lift coefficient.

If the aspect ratio of a wing is not so large and the sweep angle is larger than $15^{\circ}$, then we use the Weissenger’s L-Method to evaluate the lift coefficient of the wing.
For slender delta wings and for very low aspect ratio slender wings, analytical expressions for the lift and drag coefficients are also available. The lift coefficient for a delta wing without a camber in spanwise direction is
$$C_L=\frac{1}{2} \pi A R \alpha$$
The induced drag coefficient for delta wings having elliptical load distribution along their span is given as
$$C_{D_i}=C_L \alpha / 2$$

## 物理代写|空气动力学代写Aerodynamics代考|Compressible Steady Aerodynamics

It is a well known fact that at high speeds comparable with the speed of sound the effect of compressibility starts to play an important role on the aerodynamic characteristics of airfoil. At subsonic speeds, there exists a similarity between the compressible and incompressible external flows based on the Mach number $M=$ $U / a_{\infty}, a_{\infty}=$ free stream speed of sound. This similarity enables us to express the compressible pressure coefficient in terms of the incompressible pressure coefficient as follows
$$c_p=\frac{c_{p_o}}{\sqrt{1-M^2}}$$
Here,
$$c_{p_o}=\frac{p_o-p_{\infty}}{\frac{1}{2} \rho_{\infty} U^2}$$
is the surface pressure coefficient for the incompressible flow about a wing which is kept with a fixed thickness and span but stretched along the flow direction, $x$, with the following rule
$$x_0=\frac{x}{\sqrt{1-M^2}}, y_0=y, z_0=z$$
as shown in Fig. 1.4. The Prandtl-Glauert transformation for the wings is summarized by Eq. $1.14$ and Eq. $1.13$ is used to obtain the corresponding surface pressure coefficient. By this transformation, once we know the incompressible pressure coefficient at a point $x, y, z$, Eq. $1.13$ gives the pressure coefficient for the known free stream Mach number at the stretched coordinates $x_0, y_0, z_0$. As seen from Fig. 1.4, it is not practical to build a new plan form for each Mach number. Therefore, we need to find more practical approach in utilizing Prandtl-Glauert transformation.

For this purpose, assuming that the free stream density does not change for the both flows, we integrate Eq. $1.13$ in chord direction to obtain the same sectional lift coefficient for the incompressible and compressible flow. While doing so, if we keep the chord length same, i.e., divide $x_0$ with $\left(1-M^2\right)^{1 / 2}$, then the compressible sectional lift coefficient $c_1$ and moment coefficient $c_m$ become expressible in terms of the incompressible $c_{\mathrm{lo}}$ and $c_{\mathrm{mo}}$ as follows.

## 物理代写|空气动力学代写空气动力学代考|薄翼的稳定空气动力学

$$C_L=c_l$$

$$C_D=C_{D_o}+\frac{C_L^2}{\pi A R}$$

$$C_L=\frac{1}{2} \pi A R \alpha$$

$$C_{D_i}=C_L \alpha / 2$$

## 有限元方法代写

tatistics-lab作为专业的留学生服务机构，多年来已为美国、英国、加拿大、澳洲等留学热门地的学生提供专业的学术服务，包括但不限于Essay代写，Assignment代写，Dissertation代写，Report代写，小组作业代写，Proposal代写，Paper代写，Presentation代写，计算机作业代写，论文修改和润色，网课代做，exam代考等等。写作范围涵盖高中，本科，研究生等海外留学全阶段，辐射金融，经济学，会计学，审计学，管理学等全球99%专业科目。写作团队既有专业英语母语作者，也有海外名校硕博留学生，每位写作老师都拥有过硬的语言能力，专业的学科背景和学术写作经验。我们承诺100%原创，100%专业，100%准时，100%满意。

## MATLAB代写

MATLAB 是一种用于技术计算的高性能语言。它将计算、可视化和编程集成在一个易于使用的环境中，其中问题和解决方案以熟悉的数学符号表示。典型用途包括：数学和计算算法开发建模、仿真和原型制作数据分析、探索和可视化科学和工程图形应用程序开发，包括图形用户界面构建MATLAB 是一个交互式系统，其基本数据元素是一个不需要维度的数组。这使您可以解决许多技术计算问题，尤其是那些具有矩阵和向量公式的问题，而只需用 C 或 Fortran 等标量非交互式语言编写程序所需的时间的一小部分。MATLAB 名称代表矩阵实验室。MATLAB 最初的编写目的是提供对由 LINPACK 和 EISPACK 项目开发的矩阵软件的轻松访问，这两个项目共同代表了矩阵计算软件的最新技术。MATLAB 经过多年的发展，得到了许多用户的投入。在大学环境中，它是数学、工程和科学入门和高级课程的标准教学工具。在工业领域，MATLAB 是高效研究、开发和分析的首选工具。MATLAB 具有一系列称为工具箱的特定于应用程序的解决方案。对于大多数 MATLAB 用户来说非常重要，工具箱允许您学习应用专业技术。工具箱是 MATLAB 函数（M 文件）的综合集合，可扩展 MATLAB 环境以解决特定类别的问题。可用工具箱的领域包括信号处理、控制系统、神经网络、模糊逻辑、小波、仿真等。